U.S. patent application number 14/508230 was filed with the patent office on 2015-02-05 for bearing cooling control in an air cycle machine.
The applicant listed for this patent is Hamilton Sundstrand Corporation. Invention is credited to Eric Chrabascz, Darryl A. Colson, Seth E. Rosen.
Application Number | 20150034203 14/508230 |
Document ID | / |
Family ID | 46234687 |
Filed Date | 2015-02-05 |
United States Patent
Application |
20150034203 |
Kind Code |
A1 |
Colson; Darryl A. ; et
al. |
February 5, 2015 |
BEARING COOLING CONTROL IN AN AIR CYCLE MACHINE
Abstract
An air cycle machine has a housing which holds a compressor
section, and a turbine section having an expansion area, and a fan
section disposed outside of the housing. A shaft, which attaches to
and is coaxial with the compressor section, the turbine section and
the fan section, is supported by an air journal bearing and an air
thrust bearing. The shaft has a hollow core for porting cooling air
from the air journal bearing and the air thrust bearing, and a tube
that extends into said expansion area and communicates cooling air
from the turbine expansion area to the thrust bearing.
Inventors: |
Colson; Darryl A.; (West
Suffield, CT) ; Rosen; Seth E.; (Middletown, CT)
; Chrabascz; Eric; (Longmeadow, MA) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Hamilton Sundstrand Corporation |
Windsor Locks |
CT |
US |
|
|
Family ID: |
46234687 |
Appl. No.: |
14/508230 |
Filed: |
October 7, 2014 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
12974529 |
Dec 21, 2010 |
8905707 |
|
|
14508230 |
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Current U.S.
Class: |
138/177 |
Current CPC
Class: |
F04D 29/584 20130101;
Y10T 29/49243 20150115; F04D 29/057 20130101; F16C 37/002 20130101;
F16L 9/006 20130101 |
Class at
Publication: |
138/177 |
International
Class: |
F16L 9/00 20060101
F16L009/00 |
Claims
1. A cooling tube for an air cycle machine, the cooling tube
comprising: a tube which has a length along a curving central axis
and a width along said curving central axis, wherein said central
axis is curved at a radius of 1.3.+-.0.1 cm along an upper portion
thereof, and wherein a ratio of the length to width of the tube is
from 1.456-1.657:1.
2. The cooling tube as recited in claim 1, wherein said tube has a
width of 1.93.+-.0.076 cm along said curving central axis.
3. The cooling tube as recited in claim 2, wherein said tube has a
height of which is 2.99.+-.0.076 cm said central axis.
4. The cooling tube as recited in claim 1 wherein said tube has an
opening at a terminal end thereof for inducing air to enter said
tube.
Description
RELATED APPLICATIONS
[0001] This application is a continuation of prior U.S. application
Ser. No. 12/974,529, filed Dec. 21, 2010, the entirety of which is
herein incorporated by reference.
BACKGROUND
[0002] This application relates to air bearings incorporated into
an air cycle machine and more particularly to air seals that enable
cooling of the air bearings.
[0003] Air cycle machines are known, and may include a centrifugal
compressor driven by compressed air and a centrifugal turbine that
lowers the temperature of the compressed air. The output of the
turbine is utilized as conditioned supply air for a space or
components to be conditioned.
SUMMARY
[0004] According to an exemplar provided herein, an air cycle
machine has a housing that holds a compressor section, and a
turbine section having an expansion area, and a fan section
disposed outside of the housing. A shaft, which attaches to and is
coaxial with the compressor section, the turbine section and the
fan section, is supported by an air journal bearing and an air
thrust bearing. The shaft has a hollow core for porting cooling air
from the air journal bearing and the air thrust bearing. The shaft
also has, on an aft portion thereof, a forward opening and an aft
opening for porting cooling air into the hollow core. A tube
extends into an expansion area and communicates cooling air from
the turbine expansion area to the thrust bearing and journal
bearing.
[0005] According to an exemplar provided herein, a forward bearing
assembly for an air cycle machine has a seal having a flat outer
portion, a pair of parallel sides, the sides being attached to a
flat inner portion by an angled surface. The inner portion is
parallel to the outer portion creating a thickness therebetween. A
cylindrical pilot is disposed in an air cycle machine housing and
has a flat area for receiving the flat outer portion of the seal.
The pilot has an inner diameter wherein a ratio of the forward
pilot inner diameter to the thickness of the seal is
20.09-15.05:1.
[0006] According to an exemplar provided herein, an aft bearing
assembly for an air cycle machine has a pilot, a seal and a seal
land. The seal has a flat outer portion having a first width, a
first side wall attaching to a first side of flat inner portion via
a first angled wall, the flat inner portion having a second width
wider than the first width, a second side wall extending radially
outwardly from a second side of the inner portion via a second
angled wall, an extension attaching to the second side wall and
extending axially toward the first side wall and a radiused portion
extending from the extension and attaching to the flat outer
portion. The pilot is cylindrical and disposed in an air cycle
machine housing. The pilot has a flat area for receiving the flat
outer portion of the seal and has an inner diameter wherein a ratio
of the forward pilot inner diameter to the thickness of the seal is
10.33-8.03:1.
[0007] According to an exemplar provided herein, an air cycle
machine has a curved tube that has a length along a curving central
axis and a width along the curving central axis. The central axis
is curved at a radius R of 0.500.+-.0.04 inches (or 1.3.+-.0.1 cm)
along an upper portion thereof and a ratio of the length to width
of the tube is from 1.456-1.657:1.
[0008] According to an exemplar provided herein, a shaft for an air
cycle machine has a hollow body, a forward flange extending
radially from the hollow body, the forward flange having a first
plurality of teeth radially extending teeth disposed thereon for
cooperating with a seal, a first opening communicating with an
interior of the body, a tooth in close proximity to and aft of the
first opening, the tooth creating a barrier to air passing along
the shaft and urging the air into the first opening, a second
opening aft of the tooth and the second opening, and a second
plurality of teeth aft of the tooth, the second opening and the
first opening wherein the plurality of teeth creating a barrier to
air passing along the shaft by the tooth and urging the air into
the first opening.
[0009] According to an exemplar provided herein, a turbine housing
for an air cycle machine has an outer shell housing a compressor
section and a turbine section, and an inner shell housing a hollow
shaft, and defining an expansion area between the inner and outer
shell. The inner shell has a forward pilot having a first inner
diameter and an aft pilot having a second inner diameter wherein
the ratio between the inner diameter of the forward pilot and the
inner diameter of the aft pilot is 1.668-1.664:1. The forward pilot
and the aft pilot each have a half-tear drop shaped indentation at
an axial edge thereof.
[0010] According to an exemplar provided herein, a method of
installing a seal into an air cycle machine includes the steps of
providing a first seal having an outer diameter and a thickness
configured to engage a rotating surface wherein a ratio between the
outer diameter and the thickness is 20.09-15.05:1, providing a
housing having a first pilot having an inner diameter, and pressing
the first seal into the first pilot.
[0011] These and other features of the present invention can be
best understood from the following specification and drawings, the
following of which is a brief description.
BRIEF DESCRIPTION OF THE DRAWINGS
[0012] FIG. 1 shows a schematic of an air cycle machine
incorporating a plurality of bearing seals.
[0013] FIG. 1A shows a schematic view of bearing seal arrangement
taken along the lines A-A of FIG. 1.
[0014] FIG. 1B shows a schematic view of bearing seal arrangement
taken along the lines B-B of FIG. 1.
[0015] FIG. 2 is a perspective view of a tube used in the air cycle
machine of FIG. 1.
DETAILED DESCRIPTION
[0016] FIGS. 1, 1A and 1B, an example air cycle machine 20 ("ACM")
that may be incorporated into an air supply system (not shown) of a
vehicle, such as an aircraft, helicopter, or land-based vehicle
(not shown) is shown. The ACM 20 includes a compressor section 24,
a turbine section 26 and a fan section 28 all of which are
generally disposed about as segmented main shaft 30. The compressor
section 24 includes a compressor rotor 32. The turbine section 26
includes a turbine rotor 34, and the fan section 28 includes a fan
rotor 36. The compressor rotor 32, turbine rotor 34, and fan rotor
36 are secured on the segmented main shaft 30 that has an axially
extending tie rod 37 therewithin for co-rotation with the main
shaft about an axis A.
[0017] A forward portion 38 of the main shaft 30 has a plurality of
openings 40 to ambient and attaches to the fan rotor 36. An aft
portion 42 of the main shaft attaches to the forward portion 38 of
the main shaft 30 and has a circular, radially extending, flange 44
extending from a body 46 thereof to cooperate with a forward pilot
48. The flange 44 has three teeth 45 extending therefrom in
register with a forward seal 50 disposed on the forward pilot 48
(e.g., a flat area on the housing 90). Each of the teeth 45 has a
roughly triangular cross-section, and is nominally 0.045 in. (0.114
cm) high with a flattened upper portion 49 that is 0.010 in. (0.025
cm) wide. The ratio of height to width of each tooth 45 is about
4.5:1. An aft portion 62 of the body 46 has, a first opening 64
into the body 46 forward of a tooth 66, a second opening 68 into
the body 46 aft of the tooth 66 and a second plurality of teeth 70
aft of the opening 68. The tooth 66 and the second plurality of
teeth 70 are in register with an aft seal 71 mounted on an aft
pilot 72, as will be discussed herein. The tooth 66 and the second
plurality of teeth 70, which includes five teeth, have roughly
triangular cross-sections, are nominally .045 in high and have a
flattened upper portion 51 that is 0.010 in. (0.025 cm) wide. The
ratio of height to width of each tooth 66, 70 is about 4.5:1 to
ensure that a proper amount of air may leak through to cool the
bearings as will be discussed infra.
[0018] The ACM 20 has an aft housing (e.g., outer shell) 74 that
houses an aft air journal bearing 76, the forward and aft pilots
48, 72, the turbine section 26, the compressor section 24, the aft
portion 42 of the main shaft 30, and a thrust air bearing 78. The
forward housing 80 houses the forward portion 38 of the main shaft
30, a forward journal air bearing 82 and a forward air seal 84. The
forward housing 80 and the aft housing 74 are attached together by
bolts 86 and define an annular area 88 therebetween.
[0019] The aft housing 74 has a conical portion 90 (e.g., inner
shell) that defines on a radially outer portion thereof an
expansion area 92 for air exiting the turbine rotor 34. The conical
portion 90, on a radially inner portion thereof has the forward
pilot 48 in which the forward seal 50 is mounted the aft pilot 72
in which the aft seal 71 is mounted, and the aft journal air
bearing 76 mounted between the two seals 50, 71.
[0020] Referring now to FIG. 1A, the forward pilot 48, which is
flat and annular with a half teardrop-shaped cut-out 96 at either
end thereof, houses the forward seal 50, which may be made of a
graphite-infused polyimide material and which partially covers the
half teardrop-shaped cut-outs 96 to allow air to circulate behind
the seal to allow cooling thereof. The cut-out 96 insures that upon
machining, no impediments are left that would interfere with
mounting seal 50 on the pilot 48.
[0021] The forward pilot ID and the forward seal OD coincide at
2.410.+-.0.001 in. (6.121.+-.0.025 cm) and the seal forward has a
thickness T of 0.140.+-.0.020 in. (0.356.+-.0.051 cm), wherein the
ratio of the forward pilot ID to the thickness of the forward seal
50 is 20.09-15.05:1. The ratio insures the proper cooperation of
the seal to a plurality of teeth, in this case three (though other
numbers of teeth are contemplated), that are disposed at the end of
flange 44 attached to the main shaft 30. The forward seal 50 is
0.295.+-.0.005 in. (0.75.+-.0.012 cm) wide to ensure the teeth 45
are always in close proximity to the forward seal 50.
[0022] The forward seal 50 has a flat back portion 100, a pair of
parallel sides 102 and a top portion 104. The top portion 104,
which functions as a seal land, is joined to the sides 102 by a
pair of angled surfaces 106 that are disposed at a 40.degree. angle
relative to the back portion 100. The top portion interacts with
the forward plurality of teeth as will be discussed infra. The seal
ID is 2.246.+-.0.001 in. (5.705.+-.0.003 cm) and the ratio between
the forward seal internal diameter and the forward seal outer
diameter is 1.074-1.072:1.
[0023] Referring now to FIGS. 1B, the aft pilot 72, which is flat
and annular, houses the aft seal 71, which may be made of a
graphite-infused polyimide material. The aft pilot 72 has an ID of
1.446.+-.0.001 in. (3.67.+-.0.003 cm) and the aft seal has a
thickness T.sup.1 of 0.16.+-.0.02 in. (0.406.+-.0.051 cm), wherein
the ratio of the aft pilot ID to the thickness of the aft seal is
from 10.33-8.03:1. The ratio insures the proper cooperation of the
seal to a plurality of teeth 66, 70, in this case six (though other
numbers of teeth are contemplated), that are disposed in the body
46 of the aft portion 42 of the main shaft 30. The aft pilot 72 has
a width W of 0.500.+-.0.005 in. (1.27.+-.0.013) and the teeth 66,
70 have a height of 0.045 in. (0.114 cm) to ensure the teeth are
always in close proximity to the aft seal 71.
[0024] The aft pilot 72 is flat with a half teardrop-shaped cut-out
110 machined at either end thereof. The aft seal 71 has a flat back
portion 112 that mostly covers the half teardrop-shaped cut-outs
110, which insure that, upon machining, no impediments are left
that would interfere with mounting aft seal 71 on the pilot 72, a
forward side portion 114, a first chamfered portion 116 attaching
to the forward side portion 114, and a top portion 118, which acts
as a seal land, that interacts with the teeth 66, 70. The aft seal
71 also has an aft side portion 120 that attaches to the bottom
portion 122 via a radius portion 124 that attaches to an axially
extending portion 126. The extending portion 126 attaches to the
flat back portion 112. The aft side portion 120 attaches to the top
portion 118 via a second chamfered surface 128.
[0025] The top portion 118 interacts with the teeth 66, 70 to
minimize a flow of relatively warm air flowing past the air journal
bearing 76 into the expansion area 92. The tooth 66 blocks the air
flowing through the air journal bearing 76 that tends to be drawn
to ambient through the first hole 64 in the body 46. However, any
air flowing past the tooth 66 is induced to flow into the second
hole 68 to ambient. The plurality of teeth 70, which separates the
aft journal bearing 76 from the turbine section 26, creates a
relatively high pressure area compared to the second hole 68 to
further urge the relatively warmer air flowing from the aft air
journal bearing 76 to flow through the second hole 68 to ambient
and keep the relatively warmer air from mixing with the relatively
cool air in the turbine section 26.
[0026] The ratio between the ID of the forward seal 50 to the ID of
the aft seal 71 ranges from 1.665-1.668 to one. The ratio indicates
the relationship required by the forward and aft seal to properly
cool the thrust bearing 78 and the air journal bearing 76.
Similarly the ratio between the ID of the forward pilot 48 and the
ID of the aft pilot 72 is 1.668-1.664:1.
[0027] A forward opening 40 in shaft 30 has therein adjacent to the
forward air seal 84 to ensure that air passing through the forward
seal 50 passes to ambient through the interior of the main shaft
30. The ratio of teeth between the first and second hole and the
number of teeth aft of the second hole is about 1:5 to minimize air
flow from forward of the aft plurality of teeth to aft of the aft
plurality of teeth. Though one tooth and an array of five teeth are
shown other numbers of teeth are contemplated.
[0028] Furthermore, the ratio of the aft teeth 66, 70 to the
forward plurality of teeth 45 is about 2:1. The ratio of the
forward teeth 45 to the tooth 66 between the first and second holes
64, 68 in the segmented shaft is 3:1. These ratios aid the metering
of the correct flow of air from the thrust bearing 78 through the
air journal bearing 76 to cool those bearings.
[0029] A first bore 140 is drilled into a bottom portion 150 of the
aft housing 74 from the area 144. The first bore 140 is
0.272.+-.0.005 in. (0.691.+-.0.013 cm) thick and 1.16.+-.0.03 in.
(2.946.+-.0.076 cm) long and is drilled at angle of about
15.degree. relative to the Axis A. A second bore 146, which is
nominally 0.25 in. thick and 0.85.+-.0.03 in. (2.16 cm.+-.0.076 cm)
long past a countersunk portion 148 and is drilled at angle of
about 15.degree. relative to the Axis A and 30.degree. relative to
the first bore 140, is drilled into the bottom portion 150 of the
aft housing 74 from a turbine inlet cavity 152 to intersect the
first bore 140.
[0030] Referring to FIG. 2, a curved tube 156, which is
1.18.+-.0.03 in. (2.99.+-.0.076 cm) long along a central axis B
thereof, is 0.76.+-.0.03 in. (1.93.+-.0.076 cm) wide along a
central axis thereof and is curved at a radius R of 0.500.+-.0.04
inches (or 1.3.+-.0.1 cm) along an upper portion 158 thereof. The
tube 156 fits within the second bore 146 and has an opening 170 for
inducing air entering the turbine inlet cavity 152 to enter the
tube 156. The opening 170 is positioned into the flow of air in the
turbine inlet cavity to encourage flow into the tube 156. The ratio
of the length to width of the tube 156 is from 1.456-1.657:1 that
insures that the tube extends properly into the turbine expansion
area to draw cooling air.
[0031] Referring back to FIG. 1, air in the turbine inlet cavity
152 is captured by the tube 156 and directed through the, the
second bore 146, first bore 140 into the area 144 from which it
flows across the forward and aft sides 180, 182 of the thrust
bearing 78. Air then migrates from the aft side 182 of the thrust
bearing 78 where it is metered through the forward pilot 48 and
forward seal 50, through aft air journal bearing 76 to an aft pilot
72 and aft seal 71 where the air is dumped into the interior of the
main shaft 30 through first opening 64 or second opening 68 where
it flows through the main shaft 30 through openings 40 to ambient.
The combination of the teeth 45 in register with the forward seal
50, the teeth 66 and 70 in register with the aft seal 71, and the
first and second openings 64, 68 act to meter cooling air through
the thrust bearing 78 and the aft air journal bearing 76 as
discussed herein above. All the teeth herein 45, 66, 70 are
nominally spaced at 0.006 in. (0.015 cm) from each seal 50, 71.
[0032] Although a combination of features is shown in the
illustrated examples, not all of them need to be combined to
realize the benefits of various embodiments of this disclosure. In
other words, a system designed according to an embodiment of this
disclosure will not necessarily include all of the features shown
in any one of the Figures or all of the portions schematically
shown in the Figures. Moreover, selected features of one example
embodiment may be combined with selected features of other example
embodiments.
[0033] The preceding description is exemplary rather than limiting
in nature. Variations and modifications to the disclosed examples
may become apparent to those skilled in the art that do not
necessarily depart from the essence of this disclosure. The scope
of legal protection given to this disclosure can only be determined
by studying the following claims.
* * * * *